About the JKSPE | Browse Articles | Editorial Committe | For Reviewers | For Authors | ํ |
Sorry.
You are not permitted to access the full text of articles.
If you have any questions about permissions,
please contact the Society.
์ฃ์กํฉ๋๋ค.
ํ์๋์ ๋ ผ๋ฌธ ์ด์ฉ ๊ถํ์ด ์์ต๋๋ค.
๊ถํ ๊ด๋ จ ๋ฌธ์๋ ํํ๋ก ๋ถํ ๋๋ฆฝ๋๋ค.
HOME > Browse Articles > Current Issue
[ REGULAR ] | |
Journal of the Korean Society for Precision Engineering - Vol. 41, No. 10, pp. 789-796 | |
Abbreviation: J. Korean Soc. Precis. Eng. | |
ISSN: 1225-9071 (Print) 2287-8769 (Online) | |
Print publication date 01 Oct 2024 | |
Received 03 Jun 2024 Revised 16 Jul 2024 Accepted 23 Jul 2024 | |
DOI: https://doi.org/10.7736/JKSPE.024.066 | |
Experimental Study on Altitude Motion Control of Unmanned Waterpowered Aerial Vehicle Using Nozzle Rotation Mechanism | |
1Department of Intelligent Robot Engineering, Pukyong National University | |
2Faculty of Vehicle and Energy Engineering, Ho Chi Minh City University of Technology and Education | |
3School of Mechanical System Engineering, Division of Energy Transport System Engineering, Pukyong National University | |
4Department of Smart Mobility Engineering, Pukyong National University | |
노즐회전 메커니즘을 이용한 무인 수력 항공기의 고도 운동 제어에 관한 실험적 연구 | |
1국립부경대학교 지능로봇공학과 | |
2호치민시 기술교육대학교 자동차 및 에너지 공학부 | |
3국립부경대학교 기계시스템공학전공 | |
4국립부경대학교 스마트모빌리티공학과 | |
Correspondence to : #E-mail: thinhhuynh@pknu.ac.kr, TEL: 051-629-7991 | |
Copyright © The Korean Society for Precision Engineering This is an Open-Access article distributed under the terms of the Creative Commons Attribution Non-Commercial License (http://creativecommons.org/licenses/by-nc/3.0) which permits unrestricted non-commercial use, distribution, and reproduction in any medium, provided the original work is properly cited. | |
Funding Information ▼ |
Manned water-powered aerial vehicles have been implemented into specialized missions around water bodies, such as firefighting and rescue. However, the dual requirement of vehicle motion control and performing tasks challenges operators. Moreover, in the presence of a low visibility, dense smoke, and extreme temperature, they always face potential risks. Motivated by these difficulties, this paper proposed an unmanned water-powered aerial vehicle using a nozzle rotation mechanism. This mechanism allows the vehicle to have a wide range of forces and torques in multiple directions under constant mass flowrate condition. A simple controller was designed to investigate the fundamental flight motions and verify dynamic properties of the vehicle in practical testing. To come up with the control law, the following steps were taken. Firstly, a mathematical model was derived to reflect the vehicle’s dynamic characteristics. Secondly, a well-known proportional-derivative-integral controller incorporating gravity compensation was deployed to regulate the 3-degree-of-freedom motion system. Thirdly, experiments were conducted to confirm the flight ability of the proposed vehicle. Results demonstrated that the control system preserved stability and the vehicle could fly following the desired altitude.
Keywords: Unmanned water-powered aerial vehicle, Nozzle rotation mechanism, Altitude motion control, PID controller 키워드: 무인 수력 항공기, 노즐 회전 메커니즘, 고도 모션 제어, PID 컨트롤러 |
In the past five years, the applications of manned water-powered aerial vehicles have expanded beyond the boundary of the entertainment fields, and begun to implement into the specialized tasks, especially firefighting, rescue, and exploration. However, as can be seen from Fig. 1 [1], the work of both controlling vehicle and performing tasks brings a challenge to operators. Together with low visibility, dense smoke, and extreme temperature, their safety is usually threatened. To reduce the risk for the involved people, unmanned water-powered aerial vehicles (UWAVs) have been gradually put into development [2-6]. Like the manned type, the fundamental structural framework of these vehicles includes three main parts: a water pump, a water hose, and a board unit. The principle of operation is that the pump supplies water to the board through the flexible hose. Besides, water is jetted out at the nozzles’ outlet on the head to generate water thrust to propel the system. Additionally, there is a so-called drive mechanism used to generate proper forces and torques from this thrust, aiming to fly the vehicle.
In terms of structural design, it includes three types, which are weight-shifting [4], flow-regulating [5-7], and nozzle rotation mechanisms [2,3,7-11]. The first type uses one or more weights that slide on the head surface to adjust weight distribution, mimicking the rider’s behavior on the flyboard [12]. The second type uses multiple valves to regulate the water flow inside the head’s body so that the water thrust at the outlet nozzles can be adjusted. The final type rotates water-jet nozzles to change the direction of water thrust. Compared to the first two types, the third one outperforms in reducing vibration for the water hose and providing good controllability for the head unit [13]. However, they still have some disadvantages, such as the non-minimum phase phenomenon [7] and the very limited operating range of water-jet nozzles [2,3,8-11]. These drawbacks cause the mentioned vehicles to have low maneuverability. To overcome these disadvantages, Tri et al. [14] have investigated the UWAV using four water-jet nozzles that can be independently and widely rotated. Although this vehicle has a large angular orientation, its arrangement restricted the operating range of force, especially in the vertical axis. Therefore, the flight ability of this vehicle is predicted to be poor.
In terms of control strategies, many robust controllers have been adopted to manipulate the UWAVs, e.g. a linear servo controller [4], a nonlinear cascade sliding mode controller [5] and a robust composite controller [6]. Although the abovementioned control systems indicated robustness and tracking capabilities, their effectiveness has not been yet confirmed in reality. In practical experiments, several studies focused on investigating the fundamental movement of the UWAVs. For stabilization problems, a derivative controller [2,3,8,9], a proportional-derivative (PD) controller [10], and a robust H∞ [11] controller have been implemented for the water-powered aerial long continuum robot using multiple water-jet nozzles. However, the stability of this robot is low because of actuator saturation, i.e. the very limited operating range of nozzles in these cases. For tracking control problems, Liu et al. [7] have deployed the PD controller for a 3-DoF angular motion control system. However, the results have not been compared to any desired references. Thus, it is difficult to evaluate the control performance. Besides, Tri et al. [14] have proposed an integral super-twisting sliding mode controller incorporating an extended state observer to control the attitude of the UWAV using a nozzle rotation mechanism. The results demonstrated that the vehicle could preserve good stability and tracking performance. In the above-mentioned studies, the altitude motion tracking control of the UWAV has not yet been investigated. One can see that there are many inevitable influences such as hose fluctuation and interaction between the altitude and attitude motions. They may cause the vehicle to face resonance, leading to system instability.
Therefore, this paper proposes a vehicle using a nozzle rotation mechanism and designs a simple controller to regulate its altitude, roll, and pitch motions. Although our vehicle inherits the design of the concept of [14], it has a distinguished feature, i.e. the modification of the nozzle’s arrangement. This layout allows our vehicle to have a large range of vertical force distribution under a constant water flowrate. Thereby, the flight ability of the proposed system is expected to achieve good performance. A proportional-derivative-integral (PID) controller incorporating gravity compensation is deployed to manipulate the 3-DoF motion system. This controller is expected to drive the vehicle following a desired trajectory under the mentioned influences and external disturbances.
In summary, the main contributions of this study can be outlined as follows:
The rest of this paper is organized as follows. Section II describes the structure and mathematical model of the proposed system. Section III presents the control system design. Section IV shows the experimental results. Finally, Section V outlines conclusions.
The overall structure of the vehicle and the notations of the head assembly can be described in Figs. 2 and 3, respectively. In particular, the proposed vehicle includes three main parts namely a water pump, a flexible water hose, and a head assembly. The pump is connected to the head by the hose, to supply the water to the main distributor. The flight ability of this vehicle depends on the water force distribution, i.e. a combination of the water thrust and the direction of nozzles. Initially, water, pressurized by the pump, flows through the water inlet port on the head assembly before jetting out from the four nozzle outlet sections. These outlet ports exhibit a significantly smaller cross-sectional area compared to the inlet port, designed to accelerate the water contained inside the distributor. Consequently, water thrust is generated, propelling the vehicle. Furthermore, a swivel joint placed between the water distributor and the nozzle module allows the nozzle to rotate. These nozzles are then driven by four servos at a 1:1 ratio through a servo arm and a servo linkage. Therefore, by controlling the direction of water thrust through four independently regulated nozzles, the proposed vehicle can achieve comprehensive 6-DoF motion.
In addition, four nozzles are spaced 90 [deg] apart from the vertical axis and angled 15 [deg] relative to the vertical plane, to improve stability. Furthermore, the servos are arranged such that the nozzles can be rotated from the horizontal plane to the downward direction. Thereby, the vertical force could be adjusted from zero to the maximum available thrust.
The body-fixed frame Obxbybzb [15] and Earth-fixed frame Oxyz [16] are used to describe the proposed vehicle in the 3- dimensional space. In the first coordinate system, the x-axis, y-axis, and z-axis follows the North, East, and upward directions, respectively. The latter coordinate is placed at the center of the mass of the vehicle, which its xb-axis, yb-axis, and zb-axis point along forward, leftward, and upward directions, respectively. In addition, the kinematics of the 6-DoF vehicle can be described in the Earth-fixed frame, as follows:
(1) |
where
As can be seen from Fig. 3, the position of the ith (i = 1-4) nozzle’s outlet,
(2) |
Here, the term
(3) |
To begin with modeling, the following assumptions are made:
The head unit is mathematically described by Newton-Euler equations, as follows:
(4) |
where m is the mass of the head with its contained water and J = diag{Jbx, Jby, Jbz} is the moment of inertia matrix. On the righthand side of Eq. (3), (Fb, τb) indicate the forces and torques acting on the head, they include the gravitation force observed from the body-fixed frame with g the gravitational acceleration, the water thrust force Ft and torque τt, and external disturbances (dv, dφ) such as wind gusts, ground effects, hose effects, etc. They can be written following:
(5) |
Moreover, the water thrust forces and torques can be obtained from the differential linear momentum equation, as follows:
(6) |
(7) |
where the terms
In summary, by substituting Eqs. (5), (6), and (7) into (4), and using the kinematic relationship (1), the full dynamic equation of the proposed vehicle in the Earth-fixed frame can be achieved. However, as a first step to investigate the fundamental flight motions, the proposed vehicle is placed on the testbench, which is shown in Fig. 4, such that the longitudinal, lateral, and yaw motions are eliminated. Therefore, the 3-DoF vehicle can be derived as follows:
(8) |
where:
(9) |
and
(10) |
In the above formula Eq. (8), d represents the remaining terms after substitution and is considered as the disturbance. Additionally, the above mathematical model straightforwardly reveals that the proposed vehicle is nonlinear. Furthermore, the four controllable nozzles are used to drive the 3-DoF vehicle on the testbench, meaning the system is overactuated. One more thing, the presence of the nondiagonal elements in ε implies the proposed vehicle has an interaction between the altitude and attitude motions during the flight.
The objective of the control system is to drive the vertical position of the vehicle to follow the desired reference and to stabilize its roll and pitch angles at the equilibrium point with the smallest possible error. As a first step to address this objective, a PID controller is a proper choice because of its simplicity and intuitiveness in practical implementations.
Remark: In this system, the large-scale water pump causes unexpected issues such as low responsiveness and a lack of high precision, leading to significant delays in water thrust control. The most straightforward solution to overcome this is to keep the water flowrate constant. Thereby, the water force distribution of the vehicle depends on the nozzles’ angle.
Initially, let us define the error between the desired reference xd = [zd ϕd θd]T and the plant output x as e = xd - x. Moreover, assuming the desired reference xd is once continuously differentiable, the control law is designed as:
(11) |
where Kp, Ki, and Kd represent the controller’s gains, these gains are chosen such that the control system achieves stability. In the above formula Eq. (11), the first three terms in parentheses represent the PID controller, while the last term represents the gravity compensation. In which, the first term provides an immediate response to error. The second term eliminates the steady-state error by accumulating the difference between the desired reference and the actual plant output. The third term predicts the upcoming behavior of the error based on its rate of change. The last term compensates for the effect of gravity on the vehicle. Additionally, by substituting Eqs. (11) into (10), one gets the corresponding nozzle rotation angle vector α = [α1α2α3α4]T based on the proposed control law:
(12) |
with Q† the right inverse of Q. It is worth noting that Q ∈ R3×4 has linearly independent rows and its right-invertible matrix is given by Q† = QT(QQT)-1
In this section, the experiments are conducted on the testbench to validate the flight ability and capture the dynamic properties of the proposed vehicle under practical conditions. As can be seen from Fig. 4, the vehicle is located atop the two directional rods on the testbench, positioned 1.3 m above the ground so that the longitudinal, lateral, and yaw movements can be eliminated. The detailed systematic parameters of the vehicle are presented in the following Table 1.
Notation | Description | Value | Unit |
---|---|---|---|
J (*) | Moment of inertia | diag{41956, 41094}´10-6 |
kg.m2 |
A, a | Cross-sectional area of the inlet and outlet ports | 4.9087´10-4, 2.8274´10-5 |
m2 |
m | Mass of the head with its contained water | 8 | kg |
l, h, d | Head part dimensions | 153.159´10-3, 78.159´10-3, 98´10-3 |
m |
δ | Angle between nozzle and horizontal plane | 75 | deg |
Mass flowrate | 4.5 | kg/s |
The experiment setup is outlined in Fig. 5. In detail, the proposed controller is deployed on a 32-bit OpenRB-150 microcontroller. Operating at a clock speed of 48 MHz, this microcontroller can provide the control system with a sample time of 0.01 s. Additionally, the HC-05 Bluetooth enables wireless communication between the vehicle and a laptop equipped with an AMD Ryzen 5500U processor, 32 Gb RAM, and an NVIDIA GeForce GTX 1650 graphics card. Moreover, the baudrate for both wireless and serial communication protocols in this system is synchronized at 921.6 Kbps. Moreover, Matlab R2022b software on the laptop handles the transmission of controller parameters and reception of data from the vehicle. On the other hand, there are two sensors used to realize the 3-DoF motion of the vehicle. The first, a DT50-2 sensor placed on the top of the testbench, measures the vertical position of the head assembly. The second sensor, an MTi- 680G located on the vehicle, measures the roll and pitch angles.
In this section, the tilt angles of the head assembly are stabilized at an equilibrium point while the altitude follows the desired complex trajectory with a peak-to-peak amplitude of 0.8 m. This scenario is conducted in 72 s and described as follows:
(13) |
where z0 is an initial altitude placement above the ground and
(14) |
Additionally, the PID parameters are obtained by the trial-anderror method, as follows: Kp = diag{21.5, 100, 100}, Ki = diag{2.5, 100, 100}, Kd = diag{0.5, 10, 10}. To come up with the proper control parameters, these steps are done: First, tune the proportional gain until the head assembly begins to oscillate. Then, add the integral gain to reduce steady-state error. Finally, select an appropriately small derivative gain to improve tracking performance.
The fundamental flight motion of the vehicle within the first 72 s, namely takeoff, hovering, and landing, can be intuitively observed from Fig. 6. Especially, in the first stage a.1, the head assembly moves towards the balanced position, where the attitude angles equal zero. Then, the vehicle gradually takes off (stages a.2 to a.3) and hovers in the air at the first height of 1.3 m (stages a.3 to a.5) and then the second height of 2.1 m (stages b.6 to b.8), respectively. Finally, the vehicle lands on the ground (b.9 and b.10).
On the other hand, Figs. 7 to 9 have been provided for a comprehensive analysis of the vehicle’s flight characteristics. They are namely the motion control response of the vehicle, altitude tracking error, and control effort, respectively. Besides, note that the red dotted lines represent the desired references. In Fig. 7, one can see the PID controller can provide the system with fair stability and tracking performance. In detail, although there is a deviation from the equilibrium point at the beginning, the two roll and pitch angles of the vehicle can overall converge towards the origin by the end of the flight. Furthermore, the maximum angular oscillation amplitude is approximately ±5 deg, which falls within an acceptable range. On the other hand, the proposed vehicle can fly following the desired altitude reference with low tracking error, which can be realized clearly in Fig. 8. Additionally, the vehicle can hover in the air with very minor steady-state error observed from 40 to 55 s. In Fig. 9, at the start of takeoff, the position of the four nozzles rotates approximately 40 deg downward as a result of the gravity compensation part in the control law. Although the 1st and 3rd nozzles sometimes reach saturation at 90 deg, the overall control effort of these nozzles is consistently maintained at an average value.
However, some unexpected phenomena were observed during the flight testing. Firstly, the interaction between altitude and attitude results in fluctuations during the takeoff and landing processes of the vehicle. Besides, the large overshoots of the two angular motions are also captured, for instance, from 10 to 15 s and 60 to 75 s, respectively. Secondly, the impact of the water hose on the head assembly is evident. Especially, the water hose collides with the ground, therefore causing it to bounce at 63rd s, resulting in altitude response overshoot. Furthermore, although the head assembly itself is a symmetrical structure, the entire system, including the water hose, is not. In this case, as can be seen from Fig. 6, the initial position of the water hose is almost on the Obxbzb plane. Therefore, from 15 to 37 s, when the water jet hits the water hose, the hose will fluctuate and cause a vibration on the head assembly, especially in the longitudinal direction rather than the lateral direction. It is the main cause of oscillations in pitch motion more than roll motion.
This paper has proposed an unmanned water-powered aerial vehicle using a nozzle rotation mechanism and designed a simple 3- DoF controller to regulate its altitude, roll, and pitch movements. The vehicle aims to support the operators in specialized tasks around water bodies such as firefighting, rescue, and exploration. To achieve this, the mathematical model of the vehicle was first derived to realize its dynamic properties. They are namely nonlinearity, overactuation, and interaction between the altitude and attitude.
A well-known PID controller was then applied to govern the 3- DoF motion of the vehicle, namely altitude, roll, and pitch. The experiments were conducted to evaluate the flight capability and verify the dynamic characteristics of the proposed vehicle. The experimental results demonstrate that the vehicle can follow the desired trajectory under the influences of water hose fluctuation and the interaction between altitude and attitude.
In future work, to enhance the control performance of the system and overcome these influences, the following steps will be pursued: 1) modifying the driven mechanism to enable the nozzles to have an unlimited rotation range, and 2) applying a robust controller to compensate the vehicle’s dynamic properties and disturbances.
This work was supported in part by the National Research Foundation (NRF), South Korea, under Project BK21 FOUR (Smart Robot Convergence and Application Education Research Center); and in part by the National Research Foundation of Korea (NRF) grant funded by the Korean Government (MSIT) under Grant 2022R1A2C1003486.
1. | Dubai firefighters use jetpacks to aid high-speed response, euronews. https://www.youtube.com/watch?v=H1VIxUTzb1I |
2. | Ando, H., Ambe, Y., Ishii, A., Konyo, M., Tadakuma, K., Maruyama, S., Tadokoro, S., (2018), Aerial hose type robot by water jet for fire fighting, IEEE Robotics and Automation letters, 3(2), 1128-1135. |
3. | Ando, H., Ambe, Y., Yamaguchi, T., Yamauchi, Y., Konyo, M., Tadakuma, K., Maruyama, S., Tadokoro, S., (2020), Fire extinguishment using a 4m long flying-hose-type robot with multiple water-jet nozzles, Advanced Robotics, 34(11), 700-714. |
4. | Dinh, C.-T., Huynh, T., Kim, Y.-B., (2022), LQI control system design with GA approach for flying-type firefighting robot using waterpower and weight-shifting mechanism, Applied Science, 12(18), 9334. |
5. | Lee, D.-H., Huynh, T., Kim, Y.-B., Soumayya, C., (2021), Motion control system design for a flying-type firefighting system with water jet actuators, Actuators, 10(10), 275. |
6. | Huynh, T., Kim, Y.-B., (2023), Motion control system design for a novel water-powered aerial system for firefighting with flowregulating actuators, Drones, 7(3), 162. |
7. | Liu, X., Zhou, H., (2019), Unmanned water-powered aerial vehicles: Theory and experiments, IEEE Access, 7, 15349-15356. |
8. | Yamauchi, Y., Ambe, Y., Konyo, M., Tadakuma, K., Tadokoro, S., (2021), Passive orientation control of nozzle unit with multiple water jets to expand the net force direction range for aerial hose-type robots, IEEE Robotics and Automation Letters, 6(3), 5634-5641. |
9. | Yamauchi, Y., Ambe, Y., Konyo, M., Tadakuma, K., Tadokoro, S., (2022), Realizing large shape deformations of a flying continuum robot with a passive rotating nozzle unit that enlarges jet directions in three-dimensional space, IEEE Access, 10, 37646-37657. |
10. | Ambe, Y., Yamauchi, Y., Konyo, M., Tadakuma, K., Tadokoro, S., (2022), Stabilized controller for jet actuated cantilevered pipe using damping effect of an internal flowing fluid, IEEE Access, 10, 5238-5249. |
11. | Maezawa, Y., Ambe, Y., Yamauchi, Y., Konyo, M., Tadakuma, K., Tadokoro, S., (2023), Translational disturbance rejection for jet-actuated flying continuum robots on mobile bases, IEEE Robotics and Automation Letters, 8(11), 7456-7463. |
12. | Robinson, B., (2015), Water propelled flying board, US9145206B1. |
13. | uynh, T., Lee, D.-H., Kim, Y.-B., (2023), Study on actuator performance evaluation of aerial water-powered system for firefighting applications, Applied Sciences, 13(3), 1965. |
14. | Dinh, C.-T., Huynh, T., Lee, D.-H., Kim, Y.-B., (2023), Design and experiments of angular motion control for a novel unmanned water-powered aerial vehicle, IEEE Access, 11, 112719-112730. |
15. | Niku, S. B., (2019), Introduction to robotics: analysis, control, applications, John Wiley & Sons. |
16. | Khalil, W., Dombre, E., (2004), Modeling, identification and control of robots, Kogan Page Science. |
17. | White, F. M., (2016), Fluid Mechanics, 8th edition, McGraw- Hill. |
Ph.D. candidate in the Department of Intelligent Robot Engineering, Pukyong National University, Busan, Korea. Since 2022, he has been a Lecturer with the Faculty of Vehicle and Energy Engineering, Ho Chi Minh City University of Technology and Education, Vietnam. His research interests consist of control system, autonomous vehicle control engineering, and mobile robot.
E-mail: tridc@hcmute.edu.vn
Professor with the Department of Mechanical System Engineering, and Intelligent Robot Engineering, Pukyong National University, Busan, Korea. His research interests include control theory and application with dynamic ship positioning and autonomous control system design, etc.
E-mail: kpjiwoo@pknu.ac.kr
Assistant Professor with the Department of Smart Mobility Engineering, Pukyong National University, Busan, Korea. His research interests include control engineering, robotics, and automotive engineering.
E-mail: thinhhuynh@pknu.ac.kr
Assistant Professor with the Department of Smart Mobility Engineering, Pukyong National University, Busan, Korea. His research interests include control theory and application with control system design of marine systems.
E-mail: hun_control@pknu.ac.kr
์ฌ๋จ๋ฒ์ธ ํ๊ตญ์ ๋ฐ๊ณตํํ
(04508) ์์ธ์ ์ค๊ตฌ ์ค๋ฆผ๋ก 50-1, 12์ธต(๋ง๋ฆฌ๋ SKY1004๋น๋ฉ)
SKY 1004 Bldg. 12F, 50-1, Jungnim-ro, Jung-gu, Seoul, Republic of Korea
TEL +82-2-518-2928 l Fax +82-2-518-2937 l E-mail paper@kspe.or.kr
โ Copyright 2001 by KSPE. All Rights Reserved